JP3990985B2 - How to repair turbine blade tips - Google Patents

How to repair turbine blade tips Download PDF

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JP3990985B2
JP3990985B2 JP2002587156A JP2002587156A JP3990985B2 JP 3990985 B2 JP3990985 B2 JP 3990985B2 JP 2002587156 A JP2002587156 A JP 2002587156A JP 2002587156 A JP2002587156 A JP 2002587156A JP 3990985 B2 JP3990985 B2 JP 3990985B2
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blade
tip
rail
turbine blade
tip cap
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JP2004530827A (en
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アップデグローヴ，ケビン
バーダー，ピーター
フォスター，マイケル
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クロマロイ ガス タービン コーポレーション
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P6/00—Restoring or reconditioning objects
    • B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
    • B23P6/005—Repairing turbine components, e.g. moving or stationary blades, rotors using only replacement pieces of a particular form
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/005—Repairing methods or devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49318—Repairing or disassembling
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49718—Repairing
    • Y10T29/49721—Repairing with disassembling
    • Y10T29/4973—Replacing of defective part
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49718—Repairing
    • Y10T29/49732—Repairing by attaching repair preform, e.g., remaking, restoring, or patching
    • Y10T29/49734—Repairing by attaching repair preform, e.g., remaking, restoring, or patching and removing damaged material
    • Y10T29/49737—Metallurgically attaching preform

Description

大型の燃焼タービンエンジンで使用される高圧のタービンブレードにおいて、ブレード先端にブレード先端キャップを備え、タービンブレードは翼形（airfoil shaped）のブレード先端キャップが設けられた翼形の中空体を有する設計とすることは、比較的一般的である。ブレード先端キャップ２は、全体として、翼形の閉塞プレート３と、先端にてタービンブレードの円周の周りを伸びる先端レール（rail;横木）４とを有する（図１及び図２参照）。先端レールは、先端空所を完全に包み込むようにするか、又は、典型的に、凹状側部の後縁にスロット又は開口部を有することができる。その何れの場合でも、先端キャップ空所の周りのレールを含んで、ブレードの全長を修復することは、全ての標準的なブレード再生過程の必須の部分である。   In a high pressure turbine blade used in a large combustion turbine engine, the blade has a blade tip cap at the tip of the blade, and the turbine blade has an airfoil shaped hollow body with an airfoil shaped blade tip cap. It is relatively common to do. The blade tip cap 2 as a whole has an airfoil-shaped closing plate 3 and a tip rail 4 extending around the circumference of the turbine blade at the tip (see FIGS. 1 and 2). The tip rail can either completely enclose the tip cavity or can typically have a slot or opening at the trailing edge of the concave side. In any case, repairing the full length of the blade, including the rail around the tip cap cavity, is an integral part of all standard blade regeneration processes.

ブレードがエンジン内にて回転するとき、ブレードの先端は、エンジンケースに対し極めて狭い隙間を有し、エンジンを通って流れる気体が非効率的な仕方にてブレードの頂部の上方を流れるのを阻止する。殆どのエンジンの設計において、ブレードは、実際には、エンジンケースの摩擦面と接触する。このため、ブレード先端はかなりの程度に物理的に磨耗する。この接触が極端であるならば、その結果、先端レールが破断し又は破損する可能性がある。この型式のブレードの損傷は、任意の個々のエンジンが遭遇する作動状態と共に、ブレードの基本的設計如何に依存する。   When the blade rotates in the engine, the blade tip has a very narrow gap with respect to the engine case, preventing gas flowing through the engine from flowing above the top of the blade in an inefficient manner. To do. In most engine designs, the blade actually contacts the friction surface of the engine case. For this reason, the blade tip is physically worn to a considerable extent. If this contact is extreme, the end rail can break or break as a result. This type of blade damage depends on the basic design of the blade, as well as the operating conditions encountered by any individual engine.

先端レールがブレード先端キャップ空所の周りで特に破断し易いタービンブレードは、ブレード先端の周りに極めて高く且つ薄いレールを有する設計とされ且つ製造される。先端レールは、典型的に、高さが６．３５ｍｍ（０．２５０インチ）乃至７．６２ｍｍ（０．３００インチ）であり、肉厚は、０．３８１ｍｍ（０．０１５インチ）程度と薄い。これらブレードにおける先端レールが、エンジンの作動中に破断することは普通のことである。その破損は、新品の部品及びそれ以前に修理した部品の双方にて、また、先端レールを修復するために使用される合金の型式に関係なく生ずる。   Turbine blades whose tip rails are particularly prone to break around the blade tip cap cavity are designed and manufactured with extremely high and thin rails around the blade tips. The tip rail is typically between 6.35 mm (0.250 inches) and 7.62 mm (0.300 inches) in height and is as thin as 0.381 mm (0.015 inches). It is normal for the tip rails on these blades to break during engine operation. The failure occurs in both new and previously repaired parts and regardless of the type of alloy used to repair the tip rail.

エンジンがこの型式の難点を伴って作動することが許容される場合でさえ、影響を受けるブレードの先端に適正な隙間が存在しないため、性能は測定可能な程度に損失する。この性能の損失は、エンジンのオペレータにとって作動コストの増加となる。また、これらの損傷したブレードを修理するため、エンジンを使用箇所から除去しなければならないとき、コスト上の顕著な悪影響が及ぶ。   Even when the engine is allowed to operate with this type of difficulty, performance is lost to a measurable amount because there is no proper clearance at the tip of the affected blade. This loss of performance increases operating costs for the engine operator. Also, there is a significant cost impact when the engine must be removed from the point of use to repair these damaged blades.

発明の概要Summary of the Invention

簡単に説明すれば、ブレード先端キャップの先端レールを修復する工程と、凹状壁を先端レールの凸状壁と接続する、補強リブをブレード先端キャップを横切って取り付ける工程とを備える、タービンブレードのブレード先端キャップを修理する方法が提供される。好ましくは、補強リブは、タービンブレードのブレード先端キャップの下方にて内部リブの上方に配置される。本発明は、添付図面と共に、以下の説明を参照することにより、より容易に理解されよう。   Briefly described, a blade of a turbine blade comprising: repairing a tip rail of a blade tip cap; and connecting a concave wall with the convex wall of the tip rail and attaching a reinforcing rib across the blade tip cap. A method of repairing the tip cap is provided. Preferably, the reinforcing rib is disposed above the inner rib below the blade tip cap of the turbine blade. The invention will be more readily understood by reference to the following description in conjunction with the accompanying drawings.

発明の詳細な説明Detailed Description of the Invention

本発明は、凹状壁６を先端レール４の凸状壁７に接続する補強リブ５をブレード先端キャップを跨って組み込む工程を含むブレード先端を修理する方法を提供する（図１及び図２参照）。好ましくは、補強リブ５は、先端レール４に対し更なる強度を提供し得るように、ブレード先端キャップ２の表面下方のブレードの内部キャビティ内に鋳造された中央リブ８の上方に配置される。補強リブは、先端レールに更なる支持力を提供し得るように、従来のブレード長さの修復修理を行う間、ブレード先端内に組み込まれる。この補強リブは、先端レールの破損の問題に対するコスト効果のある解決策である。この修理方法を具体化することは、エンジンのオペレータを、さもなければエンジンの分解修理に関連する不必要な費用又は先端レールの破損に起因する性能の損失から、助ける。   The present invention provides a method for repairing the blade tip including the step of incorporating a reinforcing rib 5 that connects the concave wall 6 to the convex wall 7 of the tip rail 4 across the blade tip cap (see FIGS. 1 and 2). . Preferably, the reinforcing ribs 5 are arranged above the central rib 8 cast in the internal cavity of the blade below the surface of the blade tip cap 2 so that it can provide further strength to the tip rail 4. Reinforcing ribs are incorporated into the blade tips during conventional blade length repairs to provide additional support for the tip rail. This reinforcing rib is a cost effective solution to the problem of tip rail breakage. The implementation of this repair method helps the engine operator from unnecessary costs associated with otherwise overhauling the engine or loss of performance due to tip rail breakage.

この修理方法は、標準的な先端修理を行う間、追加的な装置を使用せずに、既存のレーザ溶接装置を利用して容易に行うことができる。新規なブレード先端キャップの形態は、ブレードの空気流、重量又は釣り合いに悪影響を及ぼすことはない。１つの特定の形態について説明したが、同一の基本的目標を実現するその他の同様の形態が可能である。例えば、補強リブは、凹状壁及凸状壁に接触するが、ブレード先端の頂部までは伸びないようにしてもよい。これと同一の修理方法は、実質的に同様のブレード先端キャップの形態を有する任意のタービンブレードに成功裏に適用することができる。   This repair method can be easily performed using existing laser welding equipment without using additional equipment during standard tip repairs. The new blade tip cap configuration does not adversely affect blade airflow, weight or balance. While one particular configuration has been described, other similar configurations are possible that achieve the same basic goal. For example, the reinforcing rib may contact the concave wall and the convex wall, but may not extend to the top of the blade tip. This same repair method can be successfully applied to any turbine blade having a substantially similar blade tip cap configuration.

ブレードの先端長さを修復するのに適した対象としてＣＦ６−５０の２段式高圧タービンブレードを決定した。次に、ブレードは、先端亀裂の溶接工程迄、標準の修理方法の全てを通じて加工した。溶接前の主要な工程は、内部の洗浄、ブレード先端の被覆の除去、真空応力除去工程、残る先端レールの大部分の除去、及びブレード先端の亀裂を除去するためのノッチング工程から成る。次に、高温度にて手で溶接することによりブレード先端の亀裂を修復した。   A CF6-50 two-stage high pressure turbine blade was determined as a suitable target for repairing the blade tip length. The blade was then processed through all of the standard repair methods up to the tip crack welding process. The main steps before welding consist of internal cleaning, blade tip coating removal, vacuum stress relief step, removal of most of the remaining tip rail, and notching step to remove blade tip cracks. Next, the crack at the blade tip was repaired by manual welding at a high temperature.

これと同時に、先端レールの残る凹状壁及び凸状壁を接続する一回の溶接パスをブレード先端キャップを亙って付与した。溶接パスは、先端キャップの表面の下方にて内部リブの頂部に直ちに配置した。全ての亀裂が修理されたことを保証するため、Ｘ線及び蛍光透過検査を行った。次に、予め加熱した相互作用可能なレーザ溶接の準備として、残るブレード先端レールを完全に平らに研磨した。   At the same time, a single welding pass for connecting the concave wall and the convex wall on which the tip rail remains was provided by rolling the blade tip cap. The weld pass was immediately placed on top of the internal ribs below the surface of the tip cap. X-ray and fluorescence transmission tests were performed to ensure that all cracks were repaired. The remaining blade tip rail was then polished completely flat in preparation for preheated interactive laser welding.

修理する間、予め加熱した相互作用レーザ溶接装置（米国特許第５，３７４，３１９号及び米国特許第５，５５４，８３７号参照）がブレード先端の円周の周りで一連のパスを溶接し、先端レール、従ってブレードの全長を修復する。本発明を具体化するため、溶接パスの各々の間、先端レール及び補強リブの表面を亙って材料を追加し得るように溶接プログラムを変更した。その結果、補強リブはブレード先端キャップと一体に溶接され、先端レールの凹状壁及び凸状壁を接続することになった（図２）。   During repair, a preheated interactive laser welding apparatus (see US Pat. No. 5,374,319 and US Pat. No. 5,554,837) welds a series of passes around the circumference of the blade tip, Repair the entire length of the tip rail and hence the blade. To embody the present invention, the welding program was modified so that material could be added over the surface of the tip rail and reinforcing ribs during each welding pass. As a result, the reinforcing rib was welded integrally with the blade tip cap and connected to the concave wall and the convex wall of the tip rail (FIG. 2).

レーザ溶接後、ブレードを最終長さまで研磨し、外部輪郭を修復した。レーザ溶接過程は精密であるため、ＥＤＭを施すこと、すなわちブレード先端キャップ空所の内部輪郭を仕上げることは、不要であった。最終的なＮＤＴ、熱処理及び被覆工程を行った。次に、ブレードに対し、破壊的金属学的分析を行った。先端溶接の構造及び完全性は受容可能であった。   After laser welding, the blade was ground to the final length to restore the external contour. Since the laser welding process is precise, it was not necessary to apply EDM, i.e. to finish the inner contour of the blade tip cap cavity. Final NDT, heat treatment and coating steps were performed. The blade was then subjected to a destructive metallurgical analysis. The structure and integrity of the tip weld is acceptable.

本発明に従って組み込まれた補強リブを示すタービンブレードの側面図である。1 is a side view of a turbine blade showing reinforcing ribs incorporated according to the present invention. FIG. 本発明によるブレード先端キャップの端面図である。1 is an end view of a blade tip cap according to the present invention.

Claims (5)

翼形の中空体及び翼形のブレード先端キャップを有し、ブレード先端キャップが翼形閉塞プレート及び閉塞プレートの上でタービンブレードの円周の周りを伸びる先端レールを有するタービンブレードを修理する方法であって、
ブレード先端キャップの先端レールを修復する工程、及び
凹状壁を先端レールの凸状壁に接続する、ブレード先端キャップを横切って補強リブを取り付ける工程とを備える、方法。A method of repairing a turbine blade having an airfoil hollow body and an airfoil blade tip cap, the blade tip cap having an airfoil closure plate and a tip rail extending around the circumference of the turbine blade on the closure plate. There,
Repairing the tip rail of the blade tip cap, and attaching a reinforcing rib across the blade tip cap connecting the concave wall to the convex wall of the tip rail. 前記補強リブはタービンブレードのブレード先端キャップの下方の内部リブの上方に配置される請求項１の方法。  The method of claim 1, wherein the reinforcing rib is disposed above an internal rib below a blade tip cap of a turbine blade. 前記先端レールは溶接により修復され、補強リブは溶接により取り付けられる請求項２の方法。  The method of claim 2, wherein the tip rail is repaired by welding and the reinforcing ribs are attached by welding. 前記補強リブは閉塞プレートから先端レールの頂部まで伸びる請求項３の方法。  4. The method of claim 3, wherein the reinforcing rib extends from the closure plate to the top of the tip rail. 前記補強リブは閉塞プレートから先端レールの頂部の下方まで伸びる請求項３の方法。  4. The method of claim 3, wherein the reinforcing rib extends from the closure plate to below the top of the tip rail.
JP2002587156A 2001-05-07 2002-02-12 How to repair turbine blade tips Expired - Fee Related JP3990985B2 (en)

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US09/850,362 US6502303B2 (en) 2001-05-07 2001-05-07 Method of repairing a turbine blade tip
PCT/US2002/005250 WO2002090039A1 (en) 2001-05-07 2002-02-12 Method of repairing a turbin blade tip

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CA2445409A1 (en) 2002-11-14
EP1385668A1 (en) 2004-02-04
EP1385668A4 (en) 2007-09-12
US6502303B2 (en) 2003-01-07
US20020162220A1 (en) 2002-11-07
WO2002090039A1 (en) 2002-11-14
CA2445409C (en) 2006-08-29
MXPA03010117A (en) 2004-03-10
JP2004530827A (en) 2004-10-07

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